CN108528699A - Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust - Google Patents

Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust Download PDF

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Publication number
CN108528699A
CN108528699A CN201810550531.6A CN201810550531A CN108528699A CN 108528699 A CN108528699 A CN 108528699A CN 201810550531 A CN201810550531 A CN 201810550531A CN 108528699 A CN108528699 A CN 108528699A
Authority
CN
China
Prior art keywords
wing
thrust
lift
compound auxiliary
screw
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201810550531.6A
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Chinese (zh)
Inventor
任曲波
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangsu Chang Exploration Robot Co Ltd
Original Assignee
Jiangsu Chang Exploration Robot Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Jiangsu Chang Exploration Robot Co Ltd filed Critical Jiangsu Chang Exploration Robot Co Ltd
Priority to CN201810550531.6A priority Critical patent/CN108528699A/en
Publication of CN108528699A publication Critical patent/CN108528699A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like
    • B64C1/30Parts of fuselage relatively movable to reduce overall size for storage
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/20Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/54Varying in area
    • B64C3/546Varying in area by foldable elements

Abstract

The present invention is a kind of hybrid lift aircraft of band expansion platform, is made of rear single-screw paddle composite wing aircraft and the compound auxiliary wing of airscrew thrust self energizing for being assemblied in its both sides;Wherein, rear single-screw paddle composite wing aircraft include body, it is foldable be mounted on body both sides hybrid lift wing, screw propeller;Wherein, body is set as deck platform;Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge;Self-enclosed ducted fan is provided in the compound auxiliary wing of airscrew thrust self energizing, the one or both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected with hybrid lift wing by wing hinge.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, the auxiliary wing using hybrid lift, low energy consumption for flight, the hang time is long, safe the features such as.

Description

Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust
Technical field
The present invention relates to a kind of aircraft, specifically a kind of rear single screw folding with the compound auxiliary wing of thrust is compound Wing manned vehicle belongs to aircraft equipment technology field.
Background technology
Existing aircraft is broadly divided into fixed-wing and vertically taking off and landing flyer(Such as helicopter and more rotors)Two major classes.When So also there is this product of VTOL fixed-wing.Traditional fixed-wing have the advantages that flying speed is fast, low energy consumption, but have It is not connected to before and after main wing and tailplane, wing structure intensity is not high, is easily damaged, and landing requires high, landing distance disadvantage; Traditional vertically taking off and landing flyer has the advantages that landing is convenient, but has that energy consumption is big, safety coefficient is low, and load capacity is poor, water Flat flying speed is slow, is easy the shortcomings of air crash;Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water The shortcomings of controllability when flat flight is not satisfactory, and that there is flight resistances is big, and energy consumption is high, and safety coefficient is not still high.
Invention content
In view of the above-mentioned problems of the prior art, the present invention not only has landing apart from short, flying speed is fast, wing knot Structure intensity height, wing can be with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area, feelings of meeting an urgent need It can play the role of aerodone under condition, greatly improve the safety of aircraft, the safety of support personnel.
To achieve the goals above, the present invention includes rear single-screw paddle composite wing aircraft, is movably arranged on compound liter The compound auxiliary wing of airscrew thrust self energizing of power aircraft both sides;Wherein, rear single-screw paddle composite wing aircraft include body, It is foldable to be mounted on body both sides hybrid lift wing, screw propeller;Wherein, body is set as deck platform;Compound liter Self-enclosed ducted fan built in power wing, hybrid lift wing outside are designed with wing hinge;Airscrew thrust self energizing is compound Self-enclosed ducted fan is provided in the auxiliary wing, the front end of the compound auxiliary wing of airscrew thrust self energizing is provided with screw propeller, The compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed ducted fan, the compound auxiliary wing of airscrew thrust self energizing One or both sides are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected with hybrid lift wing by wing hinge, In, electro-hydraulic gas interface carries lid.Manned storehouse is mounted on the lower section of body.
Further, hybrid lift wing is mounted on body both sides by the way that folding hinge is folding.
Further, propeller is a variety of dynamic structures such as electric propeller, the dynamic propeller of oil.
Further, hybrid lift wing front and back are respectively set to convex series connection head and concave series connection seat;Convex series connection head It is identical as concave series connection seat size.
Further, convex series connection head connects seat with concave as taper connection
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on hybrid lift The front and back of wing;It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space;Wherein, At least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, further include vertical tail, the vertical tail is arranged above or below body;The vertical tail is set It sets in wing both sides;The vertical tail may be implemented to fold;Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity..
Further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, It is separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing;It is reserved between the auxiliary wing of lift and the auxiliary empennage of balance free Between, the horizontal lifting rudder wing is provided in space;Wherein, at least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.
Further, it is additionally provided with engine installation position and battery/fuel on the compound auxiliary wing of airscrew thrust self energizing, In, engine is provided with power plant in installation position.
The prior art is compared, the main feature having is invented:
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, foldable pattern is used between body and both sides wing;Fold mechanism is folding hinge;After the wing expansion of both sides It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double The aircraft of quantity;Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, the auxiliary wing of modularization ducted fan drive-in hybrid lift invented uses hybrid lift, i.e., by designing in aerofoil Interior self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
4, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity, Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously The safety of row device has ensured the safety of personnel and goods and materials.
5, the present invention can realize multiple functions using hardware and software platform, modularized design,
6, the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when Lift, improve load capacity.
7, the present invention also has successive socket, and the cluster of aircraft is facilitated to fly, and further decreases cluster flight When power consumption.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with flying for long range Row, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft Middle rescue, i.e., before aircraft the dragging of faulty aircraft below is taken off, realize and mutually come to sb.'s rescue between aircraft not seen before Help phenomenon.
8. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift. Modular design reduces the disposable input of client, reduces buying and operation cost.
9. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts, And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
10. thrust device modularization can very easily realize that repair is replaced.
In 11 present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility!
13. aerofoil type energy device, efficiently uses space.
14. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Description of the drawings
Fig. 1 is the structural schematic diagram of the present invention;
Fig. 2 is the side view of the present invention;
Fig. 3 is the rearview of the present invention;
Fig. 4 is the plan view of the present invention;
Fig. 5 is the oblique view of the present invention;
In figure:101:Body;102:Hybrid lift wing;104:Self-enclosed ducted fan;105:Vertical tail;1051. vertical The rudder wing;106:Propeller;107:Energy Management System;1021:Lift main wing;1022:The horizontal lifting rudder wing;1023:Balance tail The wing;1028:Wing hinge;1001:Socket;1002:Cavity;1003:Mounting hole;1006:Battery/fuel;108:Video camera; 1026:Convex series connection head;1027:Spill series connection seat;1031, the compound auxiliary wing of airscrew thrust self energizing;10311, the auxiliary wing of lift; 10312, auxiliary empennage is balanced;1026, electro-hydraulic gas interface;10261, lid;111, engine installation position;1059:Folding hinge; 1062, screw propeller;112, manned storehouse.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figures 1 to 5, the rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust, packet The compound auxiliary wing of airscrew thrust self energizing for including rear single-screw paddle composite wing aircraft, being assemblied in its wing both sides;Wherein, institute The rear single-screw paddle composite wing aircraft stated includes body 101, the foldable hybrid lift wing mounted on 101 both sides of body 102, propeller 106;Wherein, the body 101 is set as deck platform;It is self-styled built in the hybrid lift wing 102 Ducted fan 104 is closed, 102 outside of hybrid lift wing is designed with wing hinge 1028;The airscrew thrust self energizing is multiple The front end for closing the auxiliary wing is provided with screw propeller 1062, and being internally provided with for the compound auxiliary wing of airscrew thrust self energizing is self-enclosed The one or both sides of ducted fan 104, the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge Chain 1028, and be flexibly connected with hybrid lift wing 102 by wing hinge 1028, wherein the electro-hydraulic gas interface 1036 With lid 10361, manned storehouse 112 is mounted on the lower section of body.
As further improvement of the invention, hybrid lift wing 102 is mounted on by the way that folding hinge 1059 is folding 101 both sides of body.
As further improvement of the invention, propeller 106 is screw propeller;The propeller 106 is electronic A variety of dynamic structures such as the dynamic propeller of propeller, oil.
As further improvement of the invention, 102 front and back of hybrid lift wing are respectively set to convex series connection head 1026 With concave series connection seat 1027;The convex series connection head 1026 is identical as concave series connection 1027 size of seat.
It being improved as of the invention further, convex series connection head 1026 connects seat 1027 with concave as taper connection,
As further improvement of the invention, hybrid lift wing 102 can be divided into lift main wing 1021 and balance empennage 1023 Two parts, are separately positioned on the front and back of hybrid lift wing 102;It is reserved between lift main wing 1021 and balance empennage 1023 There is space, the horizontal lifting rudder wing 1022 is provided in space;Wherein, at least there are one self-enclosed for installation inside lift main wing 1021 Ducted fan 104.
Further include vertical tail 105 as further improvement of the invention, the vertical tail 105 is arranged in body 101 Above or below;The vertical tail 105 is arranged in wing both sides;The vertical tail 105 may be implemented to fold;It is described vertical Mobilizable vertical rudder wing 1051 is installed behind empennage 105.
Improved as of the invention further, body 101 is installed with cavity 1002, in cavity 1002 installation diagram pass, fly control, The modules such as driving.
Improved as of the invention further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing of lift 10311 with And auxiliary 10,312 two parts of empennage of balance, it is separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing;The auxiliary wing of lift It is reserved with space between 10311 and the auxiliary empennage of balance 10312, the horizontal lifting rudder wing 1022 is provided in space;Wherein, lift is auxiliary At least there are one self-enclosed ducted fans 104 for installation inside the wing 10311.
As further improvement of the invention, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing 111 and battery/fuel 1006, wherein be provided with power plant in the engine installation position 111.
The prior art is compared, the main feature having is invented:
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, foldable pattern is used between body and both sides wing;Fold mechanism is folding hinge;After the wing expansion of both sides It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double The aircraft of quantity;Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, the auxiliary wing of modularization ducted fan drive-in hybrid lift invented uses hybrid lift, i.e., by designing in aerofoil Interior self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
4, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity, Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously The safety of row device has ensured the safety of personnel and goods and materials.
5, the present invention can realize multiple functions using hardware and software platform, modularized design,
6, the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when Lift, improve load capacity.
7, the present invention also has successive socket, and the cluster of aircraft is facilitated to fly, and further decreases cluster flight When power consumption.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with flying for long range Row, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft Middle rescue, i.e., before aircraft the dragging of faulty aircraft below is taken off, realize and mutually come to sb.'s rescue between aircraft not seen before Help phenomenon.
8. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift. Modular design reduces the disposable input of client, reduces buying and operation cost.
9. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts, And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
10. thrust device modularization can very easily realize that repair is replaced.
In 11 present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility!
13. aerofoil type energy device, efficiently uses space.
14. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution Similar frame mode and embodiment, are within the scope of protection of the invention.

Claims (10)

1. the rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust, which is characterized in that including rear list The compound auxiliary wing of the compound rotor aircraft of propeller type, the airscrew thrust self energizing for being assemblied in its wing both sides;
Wherein, the rear single-screw paddle composite wing aircraft includes body(101), it is foldable be mounted on body(101)Two The hybrid lift wing of side(102), propeller(106);Wherein, the body(101)It is set as deck platform;Described answers Close lifting wing(102)Built-in self-enclosed ducted fan(104), hybrid lift wing(102)Outside is designed with wing hinge (1028);Propeller(106)For screw propeller;
The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with screw propeller(1062), airscrew thrust is certainly Energize the compound auxiliary wing is internally provided with self-enclosed ducted fan(104), the side of the compound auxiliary wing of airscrew thrust self energizing or Both sides are provided with electro-hydraulic gas interface(1036)With wing hinge (1028), and pass through wing hinge (1028) and hybrid lift wing (102)Flexible connection, wherein the electro-hydraulic gas interface(1036)With lid(10361);
The manned storehouse(112)Mounted on the lower section of body.
2. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, the hybrid lift wing(102)Pass through folding hinge(1059)It is folding to be mounted on body(101)Two Side.
3. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, the propeller(106)For screw propeller;The propeller(106)It is dynamic for electric propeller, oil A variety of dynamic structures such as propeller.
4. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, the hybrid lift wing(102)Front and back are respectively set to convex series connection head(1026)It connects with concave Seat(1027);The convex series connection head(1026)It connects with concave seat(1027)Size is identical.
5. the rear single screw folding composite wing manned vehicle according to claim 3 with the compound auxiliary wing of thrust, The head it is characterized in that, convex is connected(1026)It connects with concave seat(1027)For taper connection.
6. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, the hybrid lift wing(102)Lift main wing can be divided into(1021)And balance empennage(1023)Two Part is separately positioned on hybrid lift wing(102)Front and back;Lift main wing(1021)With balance empennage(1023)Between it is pre- There are space, the horizontal lifting rudder wing is provided in space(1022);Wherein, lift main wing(1021)There are one internal at least installations Self-enclosed ducted fan(104).
7. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, further including vertical tail(105), the vertical tail(105)It is arranged in body(101)Above or below;Institute State vertical tail(105)It is arranged in wing both sides;The vertical tail(105)It may be implemented to fold;The vertical tail(105) Mobilizable vertical rudder wing is installed below(1051).
8. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, the body(101)It is installed with cavity(1002), cavity(1002)Interior installation diagram passes, flies the moulds such as control, driving Block.
9. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, the compound auxiliary wing of the airscrew thrust self energizing can be divided into the auxiliary wing of lift(10311)And the auxiliary empennage of balance (10312)Two parts are separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing;The auxiliary wing of lift(10311)With Balance auxiliary empennage(10312)Between be reserved with space, the horizontal lifting rudder wing is provided in space(1022);Wherein, the auxiliary wing of lift (10311)There are one self-enclosed ducted fans for internal at least installation(104).
10. the rear single screw folding composite wing manned vehicle according to claim 1 with the compound auxiliary wing of thrust, It is characterized in that, being additionally provided with engine installation position on the compound auxiliary wing of the airscrew thrust self energizing(111)With battery/combustion Material(1006), wherein the engine installation position(111)Inside it is provided with power plant.
CN201810550531.6A 2018-05-31 2018-05-31 Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust Pending CN108528699A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810550531.6A CN108528699A (en) 2018-05-31 2018-05-31 Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810550531.6A CN108528699A (en) 2018-05-31 2018-05-31 Rear single screw folding composite wing manned vehicle with the compound auxiliary wing of thrust

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CN108528699A true CN108528699A (en) 2018-09-14

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103935512A (en) * 2014-05-12 2014-07-23 马轶 High endurable multi-rotor craft
CN205131644U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Four -axis glide vehicle
CN206107569U (en) * 2016-09-26 2017-04-19 中国航空工业集团公司沈阳飞机设计研究所 Unmanned aerial vehicle
CN206871353U (en) * 2017-05-16 2018-01-12 许育俊 A kind of portable folding aircraft
CN107813929A (en) * 2016-09-11 2018-03-20 郎风 Combined type dalta wing duct aircraft

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103935512A (en) * 2014-05-12 2014-07-23 马轶 High endurable multi-rotor craft
CN205131644U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Four -axis glide vehicle
CN107813929A (en) * 2016-09-11 2018-03-20 郎风 Combined type dalta wing duct aircraft
CN206107569U (en) * 2016-09-26 2017-04-19 中国航空工业集团公司沈阳飞机设计研究所 Unmanned aerial vehicle
CN206871353U (en) * 2017-05-16 2018-01-12 许育俊 A kind of portable folding aircraft

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Application publication date: 20180914